Combustion turbine



Sept. 24, 1935. J. CHRISTIANSEN COMBUSTION TURBINE Filed Feb. 27, 1955 YI Smaentor JoaW/yes C/rz'sanse/a Bg Y (Ittorneg Patented Sept. 24, 1935UNITED STATES PATENT OFFICE COMBUSTION TURBINE Johannes Christiansen,Sorup-Schauby, Germany,

assignor of one-half to Alfred Oberle, Washington, D. C.,

Claims.

Ihis invention relates to turbines in general and in particular toturbines which are driven by combustion gases which may be produced bythe combustion of liquid, gaseous or pulverized fuels.

It has already been proposed to construct a turbine rotor with a numberof propeller blades having a concave driving surface and arranged so asto overlap each other on either side of the axis of rotation of therotor. In this arrangement, the driving gases were made to impinge onthe entire surface of the blade facing the inlet, but such anarrangement does not allow a very high turning moment to be obtained.

t is the object of the invention to obtain more power from the energy ofthe driving fluid by arranging propeller blades on a turbine rotor sothat they are in the best position and of the best shape to allow thegases to act upon them in the most efficient manner.

According to the invention the driving faces of the propeller blades aremade sinuous and they are so situated that the driving iluid impingessubstantially only on concave portions of this surface. Severalpropeller blades may be provided and they are arranged so that the gasesrst of all impinge upon a concave surface on one blade and are thendeflected by a convex portion on t'o a concave surface on another blade.

When the turbine is to be driven by hot gases the inlet is preferablyarranged to diverge towards the rotor so that the expansion which thusoccurs cools them and prevents the blades and the rotor in general frombeing overheated.

In order that the invention may be thoroughly understood and be morereadily carried into effect, an example of construction in accordancetherewith will now be described with reference to the accompanyingdrawing which shows diagrammatically a cross-section through the workingchamber of a turbine in accordance therewith.

The rotor consists of two discs b which are separated by two propellerblades a fixed to them and. are mounted on a shaft c in a casing g. Thedriving fluid is fed to the casing g through an inlet f and leaves thecasing g through an outlet f.

The propeller blades a are roughly semi-circular, their outside surfacesbeing quite smooth. The inside surfaces of the blades a, however, whichare the driving surfaces, are made sinuous and consist of two concaveportions e and e' joined by a convex portion d. The blades a are xed tothe discs b so as to be substantially tangential to the circumference ofthese blades at one end and to be considerably nearer the shaft c at theother end and are symmetrically disposed about the shaft c.

The driving uid which enters at f thus impinges upon the concave surfacee of one blade a and, therefore, drives the rotor in a clockwise di- 5rection. The convex portion d and the concave portion e of this blade athen deect the stream of fiuid towards the concave portion e on theother blade a, so that the rotor receives a further impulse in theclockwise direction while the gases l0 finally flow out through theoutlet f.

In this way the driving uid impinges substantially only on the concaveportions e which are farthest from the center of the rotor and theconcave portions e which are near the center of the rotor merely helpwith the convex portions d to deflect the driving gases from one blade ato the other. Thus, the blades a are positioned and shaped so that thedriving uid can do its work in the most efficient manner. It is furtherto be noted in this connection that the path of the fluid when leavingthe second blade a is substantially parallel to the path of the gasesimpinging upon the rst blade 0:.

The construction which is described is particularly useful for turbineswhich are driven by combustion gases although it is suitable forturbines driven by any uid whatever. When hot combustion gases are usedas the driving means it is inadvisable to use them while in a very hotcondition because the rotor may thus become uncomfortably overheated.Toguard against this danger the inlet f is tapered and as seen in thedrawing diverges towards the rotor so that by expansion the gases arecooled to a suitable temperature before they are used to drive therotor.

Having now particularly described and ascertained the nature of our saidinvention and in what manner the same is to be performed, we declarethat what we claim is:-

l. A turbine rotor provided with a casing and semicircular shaped bladesforming a single channel for the passage of the driving fluid saidblades being formed with sinuous surfaces and so situated that thedriving iiuid impinges substantially only on concave portions of thesinuous surface of the propeller blades.

2. A turbine rotor according to claim l, wherein the surface of thepropeller blades on which the driving fluid impinges is composed of twoconcave portions joined by a convex portion so that the driving duid isdeected by the convex portion of one blade so as to impinge on a concaveportion of another blade.

3. A turbine having a rotor according to claim l, wherein the surface ofthe propeller blades on which the driving uid impinges is composed oftwo concave portions joined by a convex portion so that the drivingfluid is deflected by the conveX portion of one blade so as to impingeon a concave portion of another blade and provided with an inletpassagefor the driving Iluid which diverges towards the rotor.

4. A turbine rotor according to claim 1, wherein the casing housing thepropeller blades has the shape of a bulbous funnel, an inlet comprisinga narrow orice thru which the driving fluid enters the turbine and adischarge opening of larger area than the inlet thru which the drivingfluid leaves the turbine.

5. A turbine driven by combustion gases having a rotor provided with twopropeller blades forming, with a housing for the blades, a singleone-Way passage for the gases, said blades having outside semicircularsurfaces of uniform curvature and sinuous inside surfaces' and which aremounted so that the driving gases impinge substantially only on concaveportions of the sinu- 10 ous faces of the propeller blades.

JOHANNES CHRISTIAN SEN.

